TY - JOUR
T1 - Torque Around Axial Direction on Rotating Detonation Engines
AU - Sawada, Satoru
AU - Goto, Keisuke
AU - Ishihara, Kazuki
AU - Kawasaki, Akira
AU - Matsuoka, Ken
AU - Kasahara, Jiro
AU - Matsuo, Akiko
AU - Funaki, Ikkoh
N1 - Funding Information:
The rotating detonation engine development was subsidized by a “Study on Innovative Detonation Propulsion Mechanism,” Research-and-Development Grant Program (Engineering) from the Institute of Space and Astronautical Science, the Japan Aerospace Exploration Agency (JAXA). The fundamental device development was subsidized by a Grant-in-Aid for Specially Promoted Research No. 19H05464, a Grant-in-Aid for Scientific Researches (A) No. 24246137, and (B) No. 17H03480 from the Japan Society for the Promotion of Science. The six-axis force sensor was manufactured by Leptorino Company, Ltd. Many laboratory members also contributed to this study; the authors thank H. Sun, H. Nakagawa, K. Hotta, M. Yamaguchi, M. Asahara, S. Ito, R. Yokoo, S. Tanaka, T. Sato, T. Noda, T. Taguchi, V. Buyakofu, and Y. Hayamizu.
Publisher Copyright:
© 2021 by Nagoya University. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission.
PY - 2022
Y1 - 2022
N2 - A rotating detonation engine (RDE) generates a continuous thrust with one or more rotating detonation waves. Because of the velocity on the order of kilometers/second, the reaction zone is relatively small. Therefore, the RDE realizes a short combustion chamber length. However, the detonation waves induce an azimuthal motion of propellant, resulting in torque around the thrust axis. Because the motion does not contribute to the thrust, the torque is important in terms of performance loss. Herein, we conducted combustion tests with a six-axis force sensor to simultaneously measure 0.149 0.009 Nm torque and 48.1 0.9 N thrust. A comparison of detonation waves captured by high-speed camera revealed that the torque followed the direction and was offset when the waves existed in both of two directions simultaneously, which indicates the possibility of controlling the torque. Under a mass flow rate at 87 9 g∕s and an equivalence ratio at 1.43 0.28, when the azimuthal component of shear force was 8.8 0.6% of the thrust, 0.77 0.10% of the total kinetic energy of the exit flow was distributed to the azimuthal component of velocity and did not contribute to the thrust. We therefore concluded that the effect of the azimuthal motion on the RDE’s performance was small.
AB - A rotating detonation engine (RDE) generates a continuous thrust with one or more rotating detonation waves. Because of the velocity on the order of kilometers/second, the reaction zone is relatively small. Therefore, the RDE realizes a short combustion chamber length. However, the detonation waves induce an azimuthal motion of propellant, resulting in torque around the thrust axis. Because the motion does not contribute to the thrust, the torque is important in terms of performance loss. Herein, we conducted combustion tests with a six-axis force sensor to simultaneously measure 0.149 0.009 Nm torque and 48.1 0.9 N thrust. A comparison of detonation waves captured by high-speed camera revealed that the torque followed the direction and was offset when the waves existed in both of two directions simultaneously, which indicates the possibility of controlling the torque. Under a mass flow rate at 87 9 g∕s and an equivalence ratio at 1.43 0.28, when the azimuthal component of shear force was 8.8 0.6% of the thrust, 0.77 0.10% of the total kinetic energy of the exit flow was distributed to the azimuthal component of velocity and did not contribute to the thrust. We therefore concluded that the effect of the azimuthal motion on the RDE’s performance was small.
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U2 - 10.2514/1.B38374
DO - 10.2514/1.B38374
M3 - Article
AN - SCOPUS:85122890279
VL - 38
SP - 59
EP - 70
JO - Journal of Propulsion and Power
JF - Journal of Propulsion and Power
SN - 0748-4658
IS - 1
ER -